A NACA 2214 airfoil has a chord 4 m. The minimum pressure coefficient at M=0 is -0.83. Find/calculate the following: a. Maximum camber in percent chord. b. Location of maximum camber in percent chord and in physical dimensions. c. Maximum thickness in percent chord and in physical dimensions. d. The minimum pressure coefficient at M=0.62. A wing at an altitude of 2500 m has an area of 40 m and a wingspan of 25 m. At 20 m/s, it produces a lift of 5000 N. It has a profile drag coefficient of 0.028. The airfoil for the wing has a lift slope of 0.11/deg. The span efficiency of the wing is 0.82. Calculate the following: a. The aspect ratio. b. The lift coefficient. c. The lift curve slope of the wing. d. The induced drag coefficient e. The total drag coefficient and the total drag f. The angle of attack needed to produce the lift coefficient if the zero-lift angle of attack of the wing is -0.7 deg A propeller has a diameter of 4.5 m. At an altitude of 1500 m, it is rotating at 900 rpm and has a forward speed of 65 m/s. The propeller has a thrust coefficient of 0.044 and a power coefficient of 0.049. Calculate the following a. The advance ratio b. The propeller efficiency c. The thrust d. The power required to spin the propeller